U.S. patent number 10,968,831 [Application Number 15/761,604] was granted by the patent office on 2021-04-06 for gas turbine and compressor module for on-shore lng plants.
This patent grant is currently assigned to NUOVO PIGNONE SRL. The grantee listed for this patent is Nuovo Pignone Tecnologie Srl. Invention is credited to Marco Giancotti.
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United States Patent |
10,968,831 |
Giancotti |
April 6, 2021 |
Gas turbine and compressor module for on-shore LNG plants
Abstract
A modular gas turbine system for on-shore LNG plants is
disclosed. The module comprises a base plate having a top side and
a bottom side and supports on the top side thereof at least a gas
turbine engine, a control and electrical room wired to the gas
turbine engine, at least part of auxiliaries of the gas turbine
engine. Additionally, at least one compressor is supported on the
base plate and mechanically coupled to the gas turbine engine and
driven into rotation by said gas turbine engine.
Inventors: |
Giancotti; Marco (Florence,
IT) |
Applicant: |
Name |
City |
State |
Country |
Type |
Nuovo Pignone Tecnologie Srl |
Florence |
N/A |
IT |
|
|
Assignee: |
NUOVO PIGNONE SRL (Florence,
IT)
|
Family
ID: |
1000005468939 |
Appl.
No.: |
15/761,604 |
Filed: |
September 26, 2016 |
PCT
Filed: |
September 26, 2016 |
PCT No.: |
PCT/EP2016/072872 |
371(c)(1),(2),(4) Date: |
March 20, 2018 |
PCT
Pub. No.: |
WO2017/055223 |
PCT
Pub. Date: |
April 06, 2017 |
Prior Publication Data
|
|
|
|
Document
Identifier |
Publication Date |
|
US 20180347469 A1 |
Dec 6, 2018 |
|
Foreign Application Priority Data
|
|
|
|
|
Sep 28, 2015 [IT] |
|
|
102015000055669 |
|
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F16M
1/04 (20130101); F01D 25/28 (20130101); F16M
5/00 (20130101); F02C 7/20 (20130101); F01D
25/285 (20130101); F02C 7/268 (20130101); F02C
7/06 (20130101); F02C 7/14 (20130101); F01D
25/12 (20130101); F01D 25/20 (20130101); F05D
2230/51 (20130101) |
Current International
Class: |
F02C
7/20 (20060101); F01D 25/28 (20060101); F16M
1/04 (20060101); F16M 5/00 (20060101); F02C
7/268 (20060101); F02C 7/14 (20060101); F01D
25/20 (20060101); F01D 25/12 (20060101); F02C
7/06 (20060101) |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
Other References
Giancotti. M. et al., Modular gas turbine plant with a heavy duty
gas turbine, GE Co-Pending Application No. FI2012A000114, filed on
Jun. 8, 2012. cited by applicant .
Italian Search Report and Written Opinion issued in connection with
corresponding IT Application No. 102015000055669 dated Jun. 13,
2016. cited by applicant .
International Search Report and Written Opinion issued in
connection with corresponding PCT Application No. PCT/EP2016/072872
dated Nov. 30, 2016. cited by applicant .
International Preliminary Report on Patentability issued in
connection with corresponding PCT Application No. PCT/EP2016/072872
dated Apr. 3, 2018. cited by applicant.
|
Primary Examiner: Kim; Craig
Attorney, Agent or Firm: Baker Hughes Patent Org.
Claims
The invention claimed is:
1. A modular gas turbine system for on-shore LNG plants, the
modular gas turbine system comprising: a base plate having a top
side and a bottom side and supporting on the top side thereof
equipment including at least a gas turbine engine, a control and
electrical room wired to the gas turbine engine, and at least one
auxiliary of the gas turbine engine; at least one compressor,
mechanically coupled to and driven by the gas turbine engine,
comprising an inlet and an outlet; an inlet duct connected to the
inlet and an outlet duct connected to the outlet; a supporting
structure extending from a ground level and having a top surface
supporting the base plate and the at least one compressor, the
supporting structure comprising an extension extending vertically
from a ground level such that the inlet duct and the outlet duct
extend between the at least one compressor and the ground
level.
2. The modular gas turbine system of claim 1, wherein the inlet
duct and the outlet duct are straight.
3. The modular gas turbine system of claim 1, wherein the at least
one compressor is supported on the base plate.
4. The modular gas turbine system of claim 1, wherein the at least
one compressor is supported on a separable base plate portion.
5. The modular gas turbine system of claim 1, further comprising an
air filter chamber fluidly connected to the gas turbine engine and
supported on the base plate.
6. The modular gas turbine system of claim 5, wherein a lubrication
oil cooler is arranged above the air filter chamber.
7. The modular gas turbine system of claim 5, wherein the control
and electrical room is arranged underneath the air filter
chamber.
8. The modular gas turbine system of claim 1, wherein the at least
one auxiliary of the gas turbine engine is selected from the group
consisting of: a gas turbine enclosure, a ventilation circuit and
ventilation fan, a helper motor, a starter motor, a fuel skid, a
water mist firefighting skid, an exhaust frame ventilation system,
a lubrication oil circuit including a lubrication oil cooler, an
oil pump, oil filters, oil mist eliminators, seal gas panel skids,
water washing skids, a dry fuel gas scrubber skid, a seal gas panel
skid, transformers, or combinations thereof.
9. The modular gas turbine system of claim 1, further comprising a
protective enclosure at least partly surrounding the equipment
supported by the base plate.
Description
The disclosure relates to gas turbine systems, specifically for
mechanical drive applications. Embodiments disclosed herein
specifically concern gas turbine systems for on-shore LNG plants,
including one or more gas compressors driven by a gas turbine
engine.
BACKGROUND OF THE INVENTION
Gas turbines are widely used as prime movers in power generation or
industrial plants, for driving electric generators or other rotary
machines, such as compressors. In off-shore installations,
compressors driven by aeroderivative gas turbines having a power
rate lower than 40 MW are often used, due to their compact
structure and reduced overall dimensions. Modularization of gas
turbines having a power rate lower than 40 MW is a quite common
practice. The gas turbine and the load are arranged on a common
frame, thus forming a single unit which is tested in the erection
and testing yard or site prior to being transported to final
destination. The common frame is then transported to final
destination and mounted on a skid. A modular arrangement of this
kind is particularly useful, since it allows complete assembling
and testing of the rotary machines prior to shipping and
installation to final destination.
Large gas turbines, both aero-derivative as well as heavy duty gas
turbines above 40 MW, are usually not modularized due to their
large dimensions. Commonly, the various components of a gas turbine
plant are transported separately from the site of manufacturing to
the final destination. The foundation is prepared at the final site
of destination and the individual machines are then mounted on the
foundation. Due to the different radial dimensions of the various
plant components, such as the gas turbine, the electric generator
and the starter, the foundation is sometimes designed with
machine-supporting surfaces at various different levels. The rotary
machines must then be aligned, mechanically connected to one
another and tuned. The entire process is extremely
time-consuming.
US2015/0184591 discloses a modularized heavy-duty gas turbine
engine for power generation, used for driving an electric
generator.
There is still a need for improvements in the field of large,
heavy-duty gas turbine engines, specifically for certain kinds of
mechanical drive applications.
BRIEF DESCRIPTION OF THE INVENTION
A modular gas turbine system for on-shore LNG (i.e. plants for the
liquefaction of natural gas) plants, is disclosed. The system
comprises:
a base plate having a top side and a bottom side and supporting on
the top side thereof at least a gas turbine engine, a control and
electrical room wired to the gas turbine engine, at least part of
auxiliaries of the gas turbine engine;
at least one compressor, mechanically coupled to the gas turbine
engine and driven into rotation by said gas turbine engine.
The module can be assembled, commissioned and tested at an
assembling, commissioning and testing site, and then shipped at the
final destination, without disassembling the major part of the
mechanical, electrical and hydraulic connections, for instance the
connections between the control and electrical room of the gas
turbine engine, such that starting the system at the final site of
use is made faster and easier, with less if no requirement for
specialized staff.
If required, some of the components of the system can be
disassembled prior to shipping, in particular if this becomes
necessary or expedient for logistic purposes. For instance, the
compressor(s) can be detached from the gas turbine engine. An
interface along the shaft line between the gas turbine engine and
the compressor(s) can be provided, which makes disconnection and
connection of the compressor to the gas turbine engine easier. In
some embodiments, a separable base plate portion can be provided,
whereon the compressor(s) is/are mounted. The separable base plate
portion can be assembled with the remaining part of the base plate
at the time of assembling, commissioning and testing. Thereafter,
the separable base plate portion can be separated from the
remaining part of the base plate and shipped separately.
Re-assembling will take place at the final site of use.
The present disclosure also concerns a method for installing a gas
turbine engine and at least one compressor driven by the gas
turbine engine on an on-shore supporting structure for an LNG
plant, comprising the following steps:
assembling at least a gas turbine engine, at least one compressor,
auxiliaries of the gas turbine engine and a control and electrical
room of the gas turbine engine on a base plate at a site of
assembling, commissioning and testing;
drivingly connecting the at least one compressor to the gas turbine
engine forming a gas turbine engine and compressor unit;
commissioning and testing the gas turbine engine and compressor
unit;
moving the base plate with the gas turbine engine, auxiliaries
thereof and control and electrical room from the site of
assembling, commissioning and testing, to a site of installation
and use, where a supporting structure extending above a ground
level is provided;
lifting the base plate and placing the base plate on the supporting
structure.
Features and embodiments are disclosed here below and are further
set forth in the appended claims, which form an integral part of
the present description. The above brief description sets forth
features of the various embodiments of the present invention in
order that the detailed description that follows may be better
understood and in order that the present contributions to the art
may be better appreciated. There are, of course, other features of
the invention that will be described hereinafter and which will be
set forth in the appended claims. In this respect, before
explaining several embodiments of the invention in details, it is
understood that the various embodiments of the invention are not
limited in their application to the details of the construction and
to the arrangements of the components set forth in the following
description or illustrated in the drawings. The invention is
capable of other embodiments and of being practiced and carried out
in various ways. Also, it is to be understood that the phraseology
and terminology employed herein are for the purpose of description
and should not be regarded as limiting.
As such, those skilled in the art will appreciate that the
conception, upon which the disclosure is based, may readily be
utilized as a basis for designing other structures, methods, and/or
systems for carrying out the several purposes of the present
invention. It is important, therefore, that the claims be regarded
as including such equivalent constructions insofar as they do not
depart from the spirit and scope of the present invention.
BRIEF DESCRIPTION OF THE DRAWINGS
A more complete appreciation of the disclosed embodiments of the
invention and many of the attendant advantages thereof will be
readily obtained as the same becomes better understood by reference
to the following detailed description when considered in connection
with the accompanying drawings, wherein:
FIG. 1 illustrates a side view of a modular gas turbine system in
an intermediate step of the process of placing the system on the
final supporting structure in the site of installation and use;
FIG. 2 illustrates a side view of the modular gas turbine system
mounted on the final supporting structure;
FIGS. 3(A)-3(D) illustrate various steps of transferring the
modular gas turbine system from a ground level to its final
position in the site of installation and use;
FIG. 4 illustrates a side view similar to FIG. 2 of a further
embodiment of the modular gas turbine system of the present
disclosure.
DETAILED DESCRIPTION OF THE INVENTION
The following detailed description of exemplary embodiments refers
to the accompanying drawings. The same reference numbers in
different drawings identify the same or similar elements.
Additionally, the drawings are not necessarily drawn to scale.
Also, the following detailed description does not limit the
invention. Instead, the scope of an embodiment defined by the
appended claims.
Reference throughout the specification to "one embodiment" or "an
embodiment" or "some embodiments" means that the particular
feature, structure or characteristic described in connection with
an embodiment is included in at least one embodiment of the subject
matter disclosed. Thus, the appearance of the phrase "in one
embodiment" or "in an embodiment" or "in some embodiments" in
various places throughout the specification is not necessarily
referring to the same embodiment(s). Further, the particular
features, structures or characteristics may be combined in any
suitable manner in one or more embodiments.
According to embodiments disclosed herein, a modular gas turbine
system 1 is provided, which comprises a base plate 3, whereon
several instrumentalities and pieces of machinery are installed.
The base plate 3 comprises top surface 3T and a bottom surface 3B.
The base plate 3 can be comprised of a lattice of longitudinal and
transversal beams. In some embodiments, the structure of the base
plate 3 can be designed as disclosed in US2015/0184591, the content
whereof is incorporated herein by reference.
On the top surface 3T of the base plate 3 a gas turbine engine 5
can be mounted. The gas turbine engine 5 can be comprised of a
compressor section 7, a combustor section 9 and a turbine section
11. The gas turbine engine 5 can comprise a heavy-duty gas turbine,
or so-called main frame turbine. The gas turbine engine can
alternatively be an aero-derivative gas turbine engine. The gas
turbine engine 5 can have a rated power of between about 40 MW and
about 150 MW. Exemplary gas turbine engines 5 that can be used in
systems according to the present disclosure can be, but are not
limited to LM6000 and LMS100 aero-derivative gas turbines, or
MS6001, MS7001 and MS9001 heavy duty gas turbines, all available
from General Electric, USA.
The gas turbine engine 5 and some of the auxiliaries thereof can be
housed in a gas turbine enclosure 12.
The inlet of the compressor section 7 is in fluid communication
with a clean-air duct 13, extending between an air filter chamber
15 and the gas turbine engine 5. In some embodiments, the air
filter chamber 15 is mounted on the same base plate 3, which
supports the gas turbine engine 5. In other embodiments, the air
filter chamber 15 can be mounted on a separate base plate or skid.
However, installing the air filter chamber 15 on the base plate 3
along with the gas turbine engine 5 can provide additional
advantages, as will become apparent from the description herein
below of a method of commissioning and installing the gas turbine
system.
The gas turbine engine 5 can be further provided with a ventilation
outlet duct 17, wherefrom exhaust cooling air from a gas turbine
enclosure is discharged. Reference number 18 designate a
ventilation fan and reference number 20 designates the ventilation
inlet duct, wherefrom ventilation air is taken by the ventilation
fan 20.
In some embodiment the gas turbine engine 5 can be provided with an
exhaust stack for discharging exhaust combustion gas in the
environment. The exhaust stack can be mounted on the same base
plate 3 along with the gas turbine engine 5. In other embodiments,
the exhaust stack can be mounted on a separate skid, which can be
supported on the base plate 3 or, on the ground level. An exhaust
duct, fluidly connecting the gas turbine engine 5 and the exhaust
stack, can be mounted on the base plate 3.
In the embodiment shown in the attached drawings, the gas turbine
engine 5 comprises an output power shaft 19, which can be
mechanically coupled to a load. In embodiments disclosed herein,
the load comprises one or more compressors. In FIGS. 1 and 2 the
load comprises a compressor train 21 comprised of a first
compressor 23 and second compressor 25. A shaft line 28 extends
from the gas turbine engine 5 to the last compressor 25.
In some embodiments, additional rotating components or machinery,
for instance additional compressors, can be arranged along the
shaft line 28. In the exemplary embodiment illustrated in the
attached drawings, a helper 27 is arranged between compressor 23
and compressor 25. The helper can be comprised of a steam turbine,
if steam is available. If the various pieces of equipment arranged
along the shaft line 28 require different rotational speeds, one or
more gear boxes or other speed manipulating devices can be located
along the shaft line 28, such that different pieces of equipment
can rotate at different speeds. The steam turbine 27, if present,
can be used as a starter motor as well. In other embodiments, an
electric machine can be provided along the shaft line 28, which can
operate as a starter, or as a helper, or both as a starter and as a
helper, if so required.
In some embodiments, not shown, both an electric machine and a
steam turbine can be arranged along the shaft line 28.
The electric machine can operate as a helper, as a generator or
both as a helper and a generator. The electric machine operating as
a helper can provide additional mechanical power to the shaft line
28, in case the gas turbine engine 5 generates insufficient
mechanical power to drive the load 21. The additional mechanical
power can be generated by converting electric power from an
electric power distribution grid, whereto the electric machine can
be connected, e.g. through a variable frequency driver.
The electric machine operating as a generator can convert a surplus
of mechanical power, generated by the gas turbine engine 5 and
exceeding the power required to drive the load 21, into electric
power, which can be delivered to the electric power distribution
grid, e.g. through a variable frequency driver, if needed.
The electric machine can be a reversible electric machine, suitable
for operating selectively as a helper or as an electric
generator.
The compressor 23, or the compressor 25, or both the compressor 23
and the compressor 25 can be provided with respective compressor
inlet and compressor outlet. In the schematic of FIGS. 1 and 2,
references 23A and 23B designate the compressor inlet and the
compressor outlet, respectively, of compressor 23. Reference
numbers 25A and 25B designate the compressor inlet and the
compressor outlet, respectively, of compressor 25. As shown in
FIGS. 1 and 2, the compressor inlets 23A, 25A and the compressor
outlets 23B, 25B are arranged on the bottom side of respective
compressor casings, such that the inlets and outlets are facing the
bottom surface 3B of the base plate 3, and therefore towards the
ground level, once the base plate 3 is arranged in the final
position of use.
In some embodiments, the compressors 23 and 25 are refrigerant
compressors for an LNG plant, to process one or more refrigerant
fluids circulating in a refrigeration cycle, to remove heat from a
flow of natural gas, which shall be liquefied for transportation
purposes.
According to some embodiments, one or both compressors 23, 25 can
be BCL-series, barrel-type centrifugal compressors. A BCL
compressor comprises a barrel with a horizontal axis and a front
closure flange. The compressor rotor, including the impellers of
the compressor, and the stationary components of the compressor,
i.e. the diaphragms forming the diffusers and the return channels,
can be extracted according to an extraction movement parallel to
the rotation axis of the compressor, i.e. parallel to the axis of
the barrel.
In other embodiments, one or both compressors 23, 25 can be
MCL-series, horizontally split centrifugal compressors. In
particular, the casing of an MCL compressor comprises two casing
portions connectable to each other along a horizontal plane. The
inner components of the compressor, i.e. the diaphragms and the
rotor, can be removed by lifting the upper casing portion, without
the need for moving the lower casing portion.
In yet further embodiments, a first one of said compressors 23, 25
can be an MCL-series, horizontally split centrifugal compressor and
the other compressor can be a BCL-series centrifugal compressor.
The BCL-series compressor can be arranged at the end of the shaft
line 28, such that the barrel can be opened and the inner
components of the compressor can be removed without dismantling the
barrel.
If the compressor train 21 comprises only one compressor, this
latter can be either a horizontally split compressor, or a BCL
compressor. In this manner, maintenance of the compressor is made
easier. Indeed, the compressor casing of any one of said
compressors of the compressor train can be opened, e.g. for
maintenance or repairing purposes, without removing the compressor
from the shaft line 28.
The inlet and outlet of said compressor(s) are arranged so to face
downwardly towards a ground level. This makes maintenance of the
compressor(s) easier. In case of MCL compressors, for instance,
since both the inlet and outlet are arranged on the lower casing
portion, the upper casing portion can be removed without
dismounting the pipes connected to the compressor inlet and
outlet.
At the same time, since the inlet and outlet of the compressor(s)
are downwardly oriented, easy access to the compressor(s) is
obtained during operation thereof. This aspect facilitates both
maintenance and safety in particular in case of emergency.
The gas turbine engine 5 is provided with a plurality of
auxiliaries and ancillary equipment, among which: turbine
enclosure, ventilation circuit and ventilation fan(s), helper
motors, e.g. electric helper motors, starter motor, fuel skid,
water mist firefighting skid, exhaust frame ventilation system,
lubrication oil circuit including a lubrication oil cooler, oil
pump, oil filters, oil mist eliminators, seal gas panel skids,
water washing skids, dry fuel gas scrubber skid, transformers and
the like.
Some or all said auxiliaries can be mounted on the base plate 3. In
the schematic of FIGS. 1 and 2, reference number 31 designates some
of the auxiliaries of the gas turbine engine 5, which are mounted
on the base plate 3.
Gas turbine engine 5 and relevant auxiliaries are controlled via
instrumentalities, which are located in a control and electrical
room 33, which can be installed on the base plate 3. In some
embodiments, the control and electrical room 33 is located under
the air-filter chamber 15, such as to reduce the overall footprint
of the apparatus and devices mounted on the base plate 3.
Additional auxiliaries can be arranged above the air-filter chamber
15, such as a lubrication oil cooler 36.
According to preferred embodiments, the above described gas turbine
system 1 can be intended for on-shore installations and can be
mounted on top of a supporting structure 41, which is provided at
the site of installation and use of the gas turbine system 1. The
supporting structure 41 can be made of concrete and can extend
above ground level GL by a height H. The supporting structure 41
can be comprised of vertical columns or uprights 43 supporting a
slab 45. A plurality of plinths 47 can project from a top surface
of the slab 45 and form a resting surface for the base plate 3 of
the gas turbine system 1. Beneath the slab 45 vertically oriented,
straight inlet and outlet ducts extend, which are fluidly coupled
to the inlet and outlet of compressors 23, 25, once the gas turbine
system 1 has been mounted on the supporting structure 41. In FIG. 2
reference numbers 49A and 49B designate the inlet duct and outlet
duct for compressor 23, respectively, while reference numbers 51A
and 51B designate the inlet duct and outlet duct for compressor 25,
respectively.
In other embodiments, the supporting structure 41 can be comprised
of vertically extending uprights or columns 43, and devoid of a
horizontal slab.
The gas turbine system 1 described so far can be assembled,
commissioned and tested at a site of assembling, commissioning and
testing. The various apparatus, devices and instrumentalities,
including the control and electrical room, the gas turbine engine,
the auxiliaries thereof and the load can be mounted on the same
base plate 3. All wiring and fluid connections required can be
completed and the system can run under load conditions.
Once commissioning and testing has been completed, the fully
modularized gas turbine system 1 can be shipped to the site of
installation and use. All the wiring and connections made when the
system has been assembled, commissioned and tested can be
maintained.
Installation of the full module on top of the supporting structure
41 can be made as shown in FIGS. 1, 2 and 3(A)-3(D) and described
herein below. The gas turbine system 1 can be transported, e.g. by
means of trailers 55, at ground level GL and brought on a side of
the supporting structure 41. For instance, the trailers 55 can be
configured and arranged to move the base plate 3 and relevant
apparatus, devices and instrumentalities supported thereon in a
direction parallel to the rotation axis of the gas turbine engine 5
and to the shaft line 28. Adjacent the supporting structure 41 a
temporary lifting structure is arranged. The temporary lifting
structure can be comprised of two rows of lifting columns 57,
between which the base plate 3 is positioned by means of trailers
55.
The base plate 3 can be provided with anchoring points 3A, whereto
lifting members 59 supported by the lifting columns 57 can be
connected. The lifting members 59 are configured and controlled to
lift the base plate 3 and relevant machinery supported on top
thereof up to a height H1, substantially corresponding to or
slightly larger than the final height at which the base plate 3
shall be positioned, when installed on the supporting structure 41.
FIGS. 3(A) and 3(B) show the lifting movement F1.
Once the base plate 3 has been brought at height H1, a set of
temporary support frames 61 is mounted underneath the base plate 3
and between the lifting columns 57. The temporary support frames 61
can comprise a plurality of uprights 63 and a horizontal overhead
floor 65, as shown in FIG. 3(C). Skid shoes 67 are provided for
resting the base plate 3 on top of the overhead floor 65.
Once the base plate 3 is placed on the top surface of the overhead
floor 65, as shown in FIGS. 1 and 3(C), the base plate 3 can be
shifted parallel to the rotation axis of the gas turbine engine 5
and moved, according to arrow F2, from the overhead floor 65 in the
final position on the supporting structure 41, as shown in FIGS. 2
and 3(D). The base plate 3 is then made to rest on the plinths and
anchored thereto and/or directly to the slab 45, while the skid
shoes 67 can be removed. The temporary support frames 61 and the
lifting columns 57 can be disassembled and removed.
Once the base plate 3 has been mounted on top of the supporting
structure 41, the compressor inlets and outlets 23A, 23B and 25A,
25B can be fluidly coupled to the vertically extending straight
inlet and outlet ducts 49A, 49B and 51A, 51B. The height H of the
supporting structure 41 is selected such that the distance between
the compressor inlets and outlets 23A, 23B and 25A, 25B and the
ground level GL is sufficient to arrange straight inlet and outlet
ducts 49A, 49B and 51A, 51B, whose axial length is a multiple N of
the respective inner diametrical dimension, wherein N is at least
3, and in some embodiments N is between 3 and 15, between 4 and 11.
The axial dimension of the straight inlet and outlet ducts allows a
more uniform gas flow profile at the compressor inlet and outlet to
be obtained, thus positively influencing the compressor efficiency,
and also reducing the flow losses due to vorticity in the gas
flow.
If the supporting structure 41 only comprises vertically extending
uprights and is devoid of a horizontal slab, the base plate 3 can
be placed on top of the supporting structure 41 using a different
system, e.g. by means of lifting cranes.
While in the above described embodiment, all the instrumentalities
of the gas turbine system 1 are installed on the base plate 3, such
that the system forms a single module which can be shipped after
commissioning and testing to the final site of installation and
use, without disconnecting any of the components forming the system
1, in other embodiments, the module can be split in two or more
sub-modules. This may be convenient or become necessary based on
existing constraints, e.g. if along the itinerary of the module,
from the site of assembling, commissioning and testing to the site
of final installation and use, limitations to the overall
dimensions or weight of the module exist. In this case, the various
components of the gas turbine system 1 can be divided into
pre-assembled units or sub-modules in a convenient manner, i.e. in
such a way as to reduce the work required for disconnecting and
re-connecting the sub-modules again.
According to some embodiments, for instance, the air-filter chamber
15 can be mounted on a separate base plate, while the remaining
components of the gas turbine system 1 are installed on one single
base plate 3. The separate base plate supporting the air-filter
chamber 15 can be mounted on the supporting structure 41, or on a
separate supporting structure, if so required, which can be placed
on the ground level, e.g. on the side of the base plate 3.
According to other embodiments, the compressor train 21, or part
thereof, can be mounted on an auxiliary, separable base plate
portion, which can be separated from the remaining base plate
3.
FIG. 4 illustrates a gas turbine system 1 according to the present
disclosure on the supporting structure 41, in a side view similar
to FIG. 2. The same reference numbers indicate the same or
equivalent components, parts or elements as shown in FIG. 2, which
are not described again herein. In FIG. 4 an auxiliary base plate
portion is schematically shown at 3C. The base plate portion 3C can
be assembled with the remaining part of the base plate 3, during
assembling, commissioning and testing. If required by logistic
constraints, the base plate portion 3C with the instrumentalities
supported thereon, in particular the compressor(s), can be
separated from the remaining of the base plate 3 after testing,
such that two sub-modules can be separately shipped at the final
destination. There the base plate portion 3C supporting the
compressor train 21 and the remaining of the base plate 3 can be
lifted and transferred on top of the supporting structure 41
separately from one another and the assembled together.
Alternatively, the base plate portion 3C can be assembled to the
remaining part of the base plate 3 prior to lifting the complete
base plate 3 in the same way as described above in connection with
FIGS. 1, 2 and 3(A)-3(D), using the same lifting columns 57 and the
same frames 61.
If the two base plate portions are lifted separately on the
structure 41, the base plate portion 3C and the remaining part of
the base plate can be lifted sequentially using the same lifting
columns 57 and frames 61. In other embodiments, two separate sets
of lifting columns 57 and frames 61 on opposite sides of the
supporting structure 41 can be used to separately lift the two base
plate portions.
The majority of the wiring and connections between the control and
electrical room on the one side and gas turbine engine 5 on the
other will be preserved, such that the time needed to re-assemble
the pre-assembled units into which the system has been split is
reduced.
If the environmental conditions in which the gas turbine system 1
will operate so require, a protective enclosure can be provided
around some or all the machinery installed on the base plate 3. For
instance, an enclosure 71 can be arranged around the compressor
train 21. The enclosure 71 can be comprised of protective panels or
similar structure, e.g. for winterizing the system, i.e. for
protecting the machinery arranged inside the enclosure 71 from
severe environmental conditions, such as extreme low temperatures,
providing a so-called winterizing protective structure.
In the embodiment of FIGS. 1 to 3 the modular gas turbine system 1
is a single deck system, wherein the machinery is arranged on the
top surface 3T of the base plate 3. In other embodiments, a
multi-deck structure can be provided. FIG. 4 illustrates by way of
example a two-deck structure, wherein above the base plate 3
uprights 81 and cross-beams 83 are provided, which can support one
or more overhead travelling cranes, schematically shown at 85. The
overhead travelling crane(s) can be used to move machinery
components on the base plate 3. The overhead traveling crane(s) and
relevant crossbeams supporting them form a second deck of the gas
turbine system 1, arranged above the first deck formed by the base
plate 3 and the relevant machinery supported thereby. The two decks
can be assembled at a site of assembling, commissioning and
testing, and then disassembled when the system 1 is shipped to the
final site of destination, where the two decks are assembled once
again. In other embodiments, the complete multi-deck system can be
shipped from the site of assembling, commissioning and testing to
the final site of destination, without disassembling and
re-assembling the two decks.
Two-deck modularized systems as shown in FIG. 4 are fully
independent, since the equipment needed for moving the various
machinery components and instrumentalities of the system are
supported by the base plate 3. In other embodiments, overhead
travelling cranes or other lifting and handling equipment can be
located in an external shed or building which houses the system 1.
In yet further embodiments, cranes and similar lifting and handling
equipment can be placed in an open space surrounding the system 1,
if sufficient room is available and if the environmental conditions
so permit.
In further embodiments, not shown, a multi-deck modular system can
be provided, wherein the rotary machines are placed on separate and
superposed decks.
While the disclosed embodiments of the subject matter described
herein have been shown in the drawings and fully described above
with particularity and detail in connection with several exemplary
embodiments, it will be apparent to those of ordinary skill in the
art that many modifications, changes, and omissions are possible
without materially departing from the novel teachings, the
principles and concepts set forth herein, and advantages of the
subject matter recited in the appended claims. Hence, the proper
scope of the disclosed innovations should be determined only by the
broadest interpretation of the appended claims so as to encompass
all such modifications, changes, and omissions. In addition, the
order or sequence of any process or method steps may be varied or
re-sequenced according to alternative embodiments.
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